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Situation Awareness and Operating in Today’s Environment
Published in Harry W. Orlady, Linda M. Orlady, John K. Lauber, Human Factors in Multi-Crew Flight Operations, 2017
Harry W. Orlady, Linda M. Orlady, John K. Lauber
Spoilers disturb the airflow over the wing, increase drag and decrease lift. Their position is an important situation awareness consideration. Spoilers must be used properly, for partial spoilers significantly reduce climb capability and full spoilers can make an airplane unflyable. Full spoilers are used only after landing in order to get the full weight of the airplane on the wheels and increase the effectiveness of braking. The use of spoilers in the air with flaps extended is prohibited with some airplanes, and in those where use of partial spoilers is approved, it is very important that the flight crew is aware of the position of the spoilers at all times. Failure to retract the spoilers when a full performance climb was indicated is thought by some to have been a factor in the American Airlines B-757 crash at Cali, Columbia.
Aircraft
Published in Milica Kalić, Slavica Dožić, Danica Babić, Introduction to the Air Transport System, 2022
Milica Kalić, Slavica Dožić, Danica Babić
Spoilers. In addition to flaps and slats, spoilers also comprise the secondary flight control system. Spoilers are metal plates hinged on the upper surface of the wings, and they act as airbrakes. The purpose of spoilers is to reduce lift and increase drag during descent and landing. Spoilers simultaneously increase drag and reduce lift. By reducing the lift-to-drag ratio after landing, spoilers transfer weight to the wheels, improving braking effectiveness. Additionally, spoilers enhance the effect of the ailerons, by disrupting the flow of air on the camber upper surface.
Early Transport Aircraft Studies
Published in G. Daniel Brewer, Hydrogen Aircraft Technology, 2017
The wing incorporates high-lift devices including 15% leading-edge slats and 35% double-slotted Fowler flaps out to the outboard engines. Conventional ailerons are fitted to the outboard wing panel. Spoilers are used in flight for direct lift control and for deceleration during landing ground run. These features are common to both the LH2 and the Jet A-fueled designs.
High-Fidelity Line Operational Simulation Evaluation of Synthetic Vision Flight Deck Technology for Enhanced Unusual Attitude Awareness and Recovery
Published in International Journal of Human–Computer Interaction, 2021
Kyle K. Ellis, Lawrence J. Prinzel, Daniel K. Kiggins, Stephanie N. Nicholas, Kathryn Ballard, Renee C. Lake, Trey J. Arthur
As the aircraft descends through 19,500 ft. to 15,000 ft. MSL to attempt a re-start of the right engine, the EICAS caution message, “SPOILER PAIRS” annunciates for 10 seconds indicating that more than two spoiler panels have failed. Approximately 60–70 seconds later, the “ROLL/YAW ASYMMETRY” caution message appears resulting from triple spoiler actuator failure (spoilers 12, 13, and 14) accompanied by a right aileron hard-over failure; this is the secondary compound event. At this time, the flight crew were hypothesized to be highly channelized in emergency descent under secondary flight control mode with only the left-side PF displays available. The presence of significant high terrain above 15,000 ft. MSL and loss of aircraft power requiring descent to re-start the right engine, created a temporally demanding and challenging situation. The right aileron hard-over failure occurrence without the primary flight control mode compensation and protections, therefore, was hypothesized to have potential to induce an unusual attitude in these conditions.
Modeling and performance evaluation of sustainable arresting gear energy recovery system for commercial aircraft
Published in International Journal of Green Energy, 2023
Jakub Deja, Iman Dayyani, Martin Skote
During the standard landing, stresses are distributed between multiple deceleration systems, including friction brakes, thrust reversers and spoilers. If the arresting gear system is implemented, all forces will be translated through the arresting hook to a landing gear. Hence, an investigation of stress distribution in the aircraft landing gear and airframe is required.